JP2004521219A - Impingement cooling system for turbine bucket platform - Google Patents
Impingement cooling system for turbine bucket platform Download PDFInfo
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- JP2004521219A JP2004521219A JP2002551268A JP2002551268A JP2004521219A JP 2004521219 A JP2004521219 A JP 2004521219A JP 2002551268 A JP2002551268 A JP 2002551268A JP 2002551268 A JP2002551268 A JP 2002551268A JP 2004521219 A JP2004521219 A JP 2004521219A
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- impingement
- platform
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- cooling
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
Abstract
本発明は、ガスタービンバケットのプラットホーム区域の冷却に関する。タービンバケット（１０）は、プラットホーム（１４）から延び、高圧及び低圧側面（３０、３２）を有する翼形部（１２）と、ホイール取付け部分（２８）と、プラットホーム（１４）とホイール取付け部分（２８）との間の半径方向位置に配置された中空のシャンク部分（２４）とを含み、プラットホームが底面（４４）を有し、複数のインピンジメント冷却孔（４８、５０、５２）を有するインピンジメント冷却プレート（３８）が、該底面から間隔を置いて中空のシャンク部分の内部に配置され、更にクロスフローの崩壊及び局部的熱伝達率の低下を減少させるように設計された、インピンジメント区域を二叉に分けるリブが設けられている。The present invention relates to cooling a platform area of a gas turbine bucket. The turbine bucket (10) extends from the platform (14) and has an airfoil (12) having high and low pressure sides (30, 32), a wheel mounting portion (28), a platform (14) and a wheel mounting portion ( 28), wherein the platform has a bottom surface (44) and has a plurality of impingement cooling holes (48, 50, 52). An impingement area, wherein an impingement area is disposed within the hollow shank portion spaced from the bottom surface and further designed to reduce cross-flow collapse and local heat transfer rate degradation. Is provided.
Description
【技術分野】
【０００１】
本発明は、ガスタービン部品の冷却に関し、より具体的には、ガスタービンバケットのプラットホーム区域の冷却に関する。
【背景技術】
【０００２】
タービンバケットは、翼形部領域と、該翼形部とそれによってバケットがタービンロータホイールに固定されるダブテールのような組立体端部との間の半径方向位置にある中空の基部すなわちシャンク部分とを含む。比較的平坦なプラットホームが、翼形部の基部に置かれて、中空のシャンク部分の上側表面又は壁面を形成する。
【０００３】
翼形部は、前縁及び後縁と、正圧側面及び負圧側面とを有する。翼形部は、高温の燃焼ガスに曝されるので、一般的に翼形部自体の内部の内部冷却回路が用いられるが、本発明の一部ではない。ここでは、関心があるのはバケットプラットホームの冷却である。
【０００４】
低サイクル疲労（ＬＣＦ）は、全てのガスタービン高圧バケットに共通の破損メカニズムの１つである。低サイクル疲労は、応力及び温度の両方の関数である。応力は、機械的負荷から生じる場合があり、或いは熱的に引き起こされる場合がある。最適の冷却方式を組み込むことによって温度勾配を減少させて部品のＬＣＦ寿命を増大させることが、ガスタービン部品の設計者が直面する課題である。
【発明の開示】
【発明が解決しようとする課題】
【０００５】
バケットの外側ガス流路側のプラットホーム区域は、高温のガス温度に曝されているが、プラットホームの底面は、ラジアルピンを通して前方ロータホイール空間から漏洩する空気のために比較的低温に曝される。プラットホームの底面と上面との間のこの温度差により、大きな熱勾配及び高い応力場が生じることになるので、プラットホーム区域における熱応力を減少させる最適の冷却方式が必要となる。
【課題を解決するための手段】
【０００６】
本発明は、バケットプラットホーム下方の中空のバケットシャンク内部に配置されたインピンジメントプレートを含む、バケットプラットホームの必要とされる冷却ハードウェアの設計における独特な方法に関する。インピンジメントプレートは、表面（すなわち、ターゲット表面）からほぼ均一な間隔を置いて配置され、かつリブによって分割された最適化されたインピンジメント冷却孔の配列を含み、それによってバケットプラットホームの正圧側面上にインピンジメント区域を形成する。
【０００７】
この冷却方法は、ホイール空間の流れにより供給される空気から成り、該空気は、インピンジメント後の流れが、プラットホーム壁面を貫通して穿孔された最適に配置されたフィルム孔の列を通して吐出されるように、プレートの方向にかつ該プレートを通して、更にバケットの正圧側面上に圧送される。
【０００８】
本発明は、孔の直径、孔の間隔、及びインピンジメントプレートの冷却されるプラットホーム底面からの最適な離間距離の最も効果的な組合せを系統的に形成することを含む。インピンジメント区域を二叉に分けるリブは、二次元クロスフローの崩壊が局部的な熱伝達率に与える影響を減少させるよう設計される。ターゲット表面を３つの異なるインピンジメント区域に細分割することは、以下の点にも役立つ。
【０００９】
（ａ）インピンジメント後の領域内の静圧変化を制御すること。
【００１０】
（ｂ）噴流とクロスストリーム流との間の運動量フラックスを制御すること。
【００１１】
（ｃ）必要とされる熱伝達率の大きさをターゲット表面の熱応力分布の変化に基づいて最適化すること。
【００１２】
インピンジメントプレートにおける冷却構成及び最適化された噴流口配列に加えて、プラットホーム壁面自体は、該壁面の厚さ構成が変化するように最適化される。プラットホームの正圧側面及び翼形部−プラットホーム間のフィレット区域における応力分布を均衡させるために、プラットホーム厚さは軸方向に沿って変化させられる。プラットホームの前縁側の厚さを一様により薄くしまたプラットホームの後縁の厚さを一様により厚くすることが、最良の構成であることが実験による検討に基づいて明らかになった。接線方向に沿ったプラットホームの厚さは、変化させてもよいし、変化させなくてもよい。
【００１３】
従って、１つの態様において、本発明は、タービンバケットに関し、該バケットは、プラットホームから延び、高圧側面及び低圧側面を有する翼形部と、ホイール取付け部分と、プラットホームとホイール取付け部分との間の半径方向位置に配置された中空のシャンク部分とを含み、プラットホームが底面を有し、複数のインピンジメント冷却孔を有するインピンジメント冷却プレートが、該底面から間隔を置いて中空のシャンク部分の内部に配置されている。
【００１４】
別の態様において、本発明は、ガスタービンバケットに関し、該ガスタービンバケットは、プラットホームから延び、高圧側面及び低圧側面を有する翼形部と、ホイール取付け部分と、底面を有するプラットホームとホイール取付け部分との間の半径方向位置に配置された中空のシャンク部分と、該底面のインピンジメント冷却を可能にするための手段と中空のシャンク部分から冷却空気を吐出するための手段とを含む。
【００１５】
更に別の態様において、本発明は、翼形部と取付け部分との間の半径方向位置に配置され、かつ中空のシャンク部分の半径方向外側壁面を形成するタービンバケット・プラットホームを冷却する方法に関し、該方法は、複数のインピンジメント冷却孔を有するインピンジメント冷却プレートを、プラットホームの底面から間隔を置いて中空のシャンク部分の内部に固定する段階と、プラットホームに吐出孔を設ける段階と、インピンジメント冷却孔とプラットホームの吐出孔とを通してタービンホイール空間の空気流を導く段階とを含む。
【発明を実施するための最良の形態】
【００１６】
図1及び図２を参照すると、タービンバケット１０は、水平でほぼ平らなプラットホーム１４から垂直方向上向きに延びる翼形部１２を含む。翼形部分は、前縁１５及び後縁１７を有する。プラットホーム１４の下方には、バケットの根元すなわちシャンク部分２４の前縁側面２０及び後縁側面２２から反対方向に延びる２対のいわゆる「天使の翼」がある。プラットホーム１４は、シャンク部分２４に結合されかつ該シャンク部分の一部を形成し、該シャンク部分２４はまた、側壁又はスカート２６を含む。中空のシャンク部分の下方には、ダブテール２８（一部のみが図示される）があり、該ダブテール２８によってバケットがタービンホイール（好ましい実施形態において、ガスタービンの第１段又は第２段ホイール）に固定される。
【００１７】
翼形部１２は、高圧側面３０及び低圧側面３２を有し、従って、プラットホーム１４もまた高圧側面３４及び低圧側面３６を有する。中空のシャンク部分２６が、プラットホームのすぐ半径方向下方に配置され、この中空のシャンク部分の内部において、インピンジメントプレート３８が、プラットホームの底面４４上の、該プレートの外周に一致する一体の棚部又は肩部４０、４２（図４参照）に沿って、シャンク部分の内部に固定（ろう付け又は他の適当な手段により）される。図３に示すように、インピンジメントプレートは、プラットホーム１４の底面４４に比較的に近接し、また該底面４４にほぼ一致しており、インピンジメントプレート３８とプラットホーム１４の底面４４との間の間隔が、ほぼ一定に保たれるようになっている。
【００１８】
インピンジメントプレート３８は、その平面図を示す図３に最も良く見られる。プレート４０は、その厚さがプラットホーム底面と該プレートとの間の間隔に一致している直立リブ４６によりほぼ二叉に分けられている。このような間隔は、約０．１０インチから０．３０インチの間、好ましくは約０．２０インチとすることができる。
【００１９】
プレート３８には、翼形部に最も近接するインピンジメント孔又は噴流口４８の第１の配列又は区域と、翼形部から遠く離れたリブ４６の他方側におけるインピンジメント孔又は噴流口５０の第２の配列又は区域と、翼形部の後縁１７の直近にあるプレート３８のコーナ部におけるインピンジメント孔又は噴流口５２の第３の配列又は区域とが形成される。図３から分かるように、これら３つの孔の配列は、プラットホーム１４に形成されたフィルム冷却孔５６の配列のすぐ下方に位置するプレートの空白域５４を囲んでおり、このフィルム冷却孔５６の配列は、プレート３８のインピンジメント孔とプラットホーム１４のフィルム孔との間の空間的関係の理解を容易にするために、図３において仮想線で示されている。図３には、インピンジメント孔の全てが示されているわけではなく、またそれら孔が一定の尺度で図示されてもいないことを理解されたい。それにもかかわらず、線５８、６０、及び６２の配列は、それぞれの配列の各々における孔の列の中心線を表す。流れの矢印６４は、インピンジメントプレート３８を通過した後にプラットホームの底部に沿ってプラットホーム１４のフィルム冷却孔５６における吐出位置に向かう冷却空気の流れの方向を示す。
【００２０】
各配列内の孔は、所定の列において「翼幅」方向に互いに間隔を置いて配置されると同時に、列自体は「流線」方向に間隔を置いて配置される。特定の用途に応じて、両方向における間隔を変えることができる。１つの実施例では、流線方向における列の間隔は、０．１６から０．４３インチの間で変えることができる。翼幅方向における孔の間隔は、０．１４から０．２７インチの間で変えることができる。
【００２１】
インピンジメントプレートのインピンジメント冷却孔４８、５０、５２の全てが、該プレートの上面及び下面に対して垂直に穿孔され、約０．０２０インチの直径を有することができる。フィルム冷却孔５６は、ある角度で傾斜させてプラットホームを貫通して穿孔されて、プラットホーム表面への付着を促進し、従って付加的な冷却機能を与える。
【００２２】
インピンジメント孔の直径、翼幅方向及び流線方向の両方向の間隔、並びにインピンジメントプレート３８とプラットホーム１４の底面４４との間の最適な離間距離を賢明に選択することによって、幾つかの利点が得られる。例えば、インピンジメントプレートにわたる全圧力損失を、最小限にすることができ、また運動量フラックスを制御することによっても（噴流口の配列構成のクロスフローの崩壊への影響を減らすことにより）、ターゲット表面（すなわち底面４４）における高い熱伝達率分布を達成することができる。
【００２３】
更に、孔４８、５０、５２のそれぞれの配列によって形成されるインピンジメント区域を二叉に分けるリブ４６を組み込むことにより、二次元クロスフローの崩壊が局部的な熱伝達率に与える影響を減少させる。このことはまた、回転場の影響による遠心荷重だけでなく、プレート４０にわたる圧力比による該プレートの変形を減少させるのにも役立つ。
【００２４】
冷却構成及び最適化された噴流口配列及びインピンジメントプレート構成に加えて、プラットホーム１４自体の壁面が、該壁面の厚さ構成を変化させることによって最適化される。プラットホームの正圧側面及び翼形部−プラットホーム間のフィレット区域における応力分布を均衡させるために、プラットホームの厚さが、図１に最も良く見られるように軸方向に沿って変化させられる。プラットホームの前縁側の厚さを一様により薄く（例えば、０．１６０インチ）し、プラットホームの後縁の厚さを一様により厚く（例えば、０．３８０インチ）し、プラットホームの中央部の周りではそれらの厚さの間で変化させることが、最良の構成であることが実験による検討に基づいて明らかになった。
【００２５】
この特定のプラットホームの幾何学形状構成を上述の冷却配置に組み合わせることよって、最良のＬＣＦ寿命が得られると思われる。
【００２６】
現在最も実用的かつ好ましい実施形態であると考えられるものに関して本発明を説明してきたが、本発明は、開示した実施形態に限定されるべきではなく、逆に、特許請求の範囲の技術思想及び技術的範囲内に含まれる様々な変更形態及び均等の構成を保護しようとするものであることを理解されたい。
【図面の簡単な説明】
【００２７】
【図１】バケットの中空のシャンク部分内部のインピンジメントプレートを示す、ガスタービンバケットの一部断面の部分正面図。
【図２】バケットのシャンク部分内部のインピンジメントプレートを全体的に仮想線で示す、図１に示したバケットの平面図。
【図３】本発明によるインピンジメントプレートの平面図。
【図４】図２に示したバケットの部分側面断面図。
【符号の説明】
【００２８】
１０ タービンバケット
１２ 翼形部
１４ プラットホーム
１５ 翼形部前縁
１６、１８ 天使の翼
１７ 翼形部後縁
２４ シャンク部分
２６ スカート
２８ ダブテール
３８ インピンジメント冷却プレート
４４ プラットホームの底面
４６ リブ
５０ インピンジメント冷却孔【Technical field】
[0001]
The present invention relates to cooling gas turbine components, and more particularly, to cooling a platform area of a gas turbine bucket.
[Background Art]
[0002]
The turbine bucket includes an airfoil region and a hollow base or shank portion at a radial position between the airfoil and an assembly end, such as a dovetail, by which the bucket is secured to the turbine rotor wheel. including. A relatively flat platform is placed at the base of the airfoil to form the upper surface or wall of the hollow shank portion.
[0003]
The airfoil has a leading edge and a trailing edge, and a pressure side and a suction side. Because the airfoil is exposed to the hot combustion gases, an internal cooling circuit is typically used within the airfoil itself, but is not part of the present invention. Here, what is of interest is the cooling of the bucket platform.
[0004]
Low cycle fatigue (LCF) is one of the failure mechanisms common to all gas turbine high pressure buckets. Low cycle fatigue is a function of both stress and temperature. Stress may result from mechanical loading or may be thermally induced. Reducing the temperature gradient and increasing the LCF life of a component by incorporating an optimal cooling scheme is a challenge faced by gas turbine component designers.
DISCLOSURE OF THE INVENTION
[Problems to be solved by the invention]
[0005]
The platform area on the outer gas flow path side of the bucket is exposed to high gas temperatures, but the bottom surface of the platform is exposed to relatively low temperatures due to air leaking from the forward rotor wheel space through the radial pins. This temperature difference between the bottom and top surfaces of the platform results in large thermal gradients and high stress fields, requiring an optimal cooling scheme to reduce thermal stress in the platform area.
[Means for Solving the Problems]
[0006]
The present invention relates to a unique method in designing the required cooling hardware of a bucket platform, including an impingement plate located inside a hollow bucket shank below the bucket platform. The impingement plate is substantially uniformly spaced from the surface (i.e., the target surface) and includes an optimized array of impingement cooling holes separated by ribs, thereby providing a pressure side of the bucket platform. Form an impingement area on top.
[0007]
This cooling method consists of air supplied by a flow in the wheel space, the air after impingement being discharged through an optimally arranged row of film holes drilled through the platform wall. As such, it is pumped in the direction of and through the plate and onto the pressure side of the bucket.
[0008]
The present invention involves systematically forming the most effective combination of hole diameter, hole spacing, and optimal spacing of the impingement plate from the bottom of the cooled platform. The ribs that bifurcate the impingement area are designed to reduce the effect of the collapse of the two-dimensional crossflow on the local heat transfer coefficient. Subdividing the target surface into three different impingement areas also helps:
[0009]
(A) Controlling static pressure changes in the region after impingement.
[0010]
(B) controlling the momentum flux between the jet and the cross-stream flow;
[0011]
(C) Optimizing the required heat transfer coefficient based on the change in the thermal stress distribution on the target surface.
[0012]
In addition to the cooling arrangement and the optimized jet arrangement in the impingement plate, the platform wall itself is optimized such that the wall thickness configuration changes. The platform thickness is varied along the axial direction to balance the stress distribution in the pressure side of the platform and in the airfoil-platform fillet area. Experimental investigations have shown that the best configuration is to make the thickness of the leading edge side of the platform evenly thinner and the thickness of the trailing edge of the platform evenly thicker. The thickness of the platform along the tangential direction may or may not be changed.
[0013]
Accordingly, in one aspect, the present invention relates to a turbine bucket, the bucket extending from the platform, having an airfoil having high and low pressure sides, a wheel mounting portion, and a radius between the platform and the wheel mounting portion. An impingement cooling plate having a bottom surface and a plurality of impingement cooling holes disposed within the hollow shank portion spaced from the bottom surface. Have been.
[0014]
In another aspect, the invention relates to a gas turbine bucket, the gas turbine bucket extending from a platform, having an airfoil having high and low pressure sides, a wheel mounting portion, and a platform and wheel mounting portion having a bottom surface. And a means for allowing impingement cooling of the bottom surface and means for discharging cooling air from the hollow shank portion.
[0015]
In yet another aspect, the present invention relates to a method of cooling a turbine bucket platform disposed at a radial location between an airfoil and a mounting portion and forming a radially outer wall surface of a hollow shank portion. The method comprises the steps of: fixing an impingement cooling plate having a plurality of impingement cooling holes inside a hollow shank portion spaced from a bottom surface of the platform; providing a discharge hole in the platform; Directing airflow in the turbine wheel space through the holes and the discharge holes of the platform.
BEST MODE FOR CARRYING OUT THE INVENTION
[0016]
Referring to FIGS. 1 and 2, the turbine bucket 10 includes an airfoil 12 extending vertically upward from a horizontal, substantially flat platform 14. The airfoil has a leading edge 15 and a trailing edge 17. Beneath the platform 14 are two pairs of so-called "angel wings" extending in opposite directions from the leading edge side 20 and trailing edge side 22 of the bucket root or shank portion 24. Platform 14 is coupled to and forms a part of shank portion 24, which also includes a side wall or skirt 26. Below the hollow shank portion is a dovetail 28 (only part of which is shown) that allows the bucket to be attached to a turbine wheel (in a preferred embodiment, a first or second stage gas turbine wheel). Fixed.
[0017]
The airfoil 12 has a high pressure side 30 and a low pressure side 32, and thus the platform 14 also has a high pressure side 34 and a low pressure side 36. A hollow shank portion 26 is located just radially below the platform, inside which the impingement plate 38 has an integral ledge on the platform bottom surface 44 that conforms to the perimeter of the plate. Or fixed (by brazing or other suitable means) along the shoulders 40, 42 (see FIG. 4) inside the shank portion. As shown in FIG. 3, the impingement plate is relatively close to and substantially coincides with the bottom surface 44 of the platform 14, and a gap between the impingement plate 38 and the bottom surface 44 of the platform 14. , But is kept almost constant.
[0018]
The impingement plate 38 is best seen in FIG. 3, which shows a plan view thereof. Plate 40 is substantially bifurcated by upstanding ribs 46 whose thickness matches the spacing between the platform bottom surface and the plate. Such spacing may be between about 0.10 inches and 0.30 inches, preferably about 0.20 inches.
[0019]
Plate 38 includes a first array or section of impingement holes or jets 48 closest to the airfoil and a first array of impingement holes or jets 50 on the other side of rib 46 remote from the airfoil. A second array or section is formed, and a third array or section of impingement holes or jets 52 at the corners of the plate 38 immediately adjacent the trailing edge 17 of the airfoil. As can be seen from FIG. 3, the arrangement of these three holes surrounds a blank area 54 of the plate located immediately below the arrangement of film cooling holes 56 formed in the platform 14, and this arrangement of film cooling holes 56. Is shown in phantom in FIG. 3 to facilitate understanding of the spatial relationship between the impingement holes in plate 38 and the film holes in platform 14. It should be understood that not all of the impingement holes are shown in FIG. 3 and that the holes are not shown to scale. Nevertheless, the arrangement of lines 58, 60, and 62 represents the centerline of the row of holes in each of the respective arrangements. The flow arrow 64 indicates the direction of the flow of cooling air after passing through the impingement plate 38 and along the bottom of the platform toward a discharge location in the film cooling holes 56 of the platform 14.
[0020]
The holes in each array are spaced from one another in the "span" direction in a given row, while the rows themselves are spaced in the "streamline" direction. The spacing in both directions can be varied depending on the particular application. In one embodiment, the row spacing in the streamline direction can vary between 0.16 and 0.43 inches. The hole spacing in the span direction can vary between 0.14 and 0.27 inches.
[0021]
All of the impingement cooling holes 48, 50, 52 of the impingement plate are drilled perpendicular to the upper and lower surfaces of the plate and can have a diameter of about 0.020 inches. Film cooling holes 56 are drilled through the platform at an angle to facilitate adhesion to the platform surface and thus provide additional cooling.
[0022]
By judiciously choosing the diameter of the impingement holes, the spanwise and streamline spacing, and the optimal separation between the impingement plate 38 and the bottom surface 44 of the platform 14, several advantages are provided. can get. For example, the total pressure drop across the impingement plate can be minimized, and by controlling the momentum flux (by reducing the impact of the orifice arrangement on the cross-flow collapse), A high heat transfer coefficient distribution at (i.e., the bottom surface 44) can be achieved.
[0023]
Further, by incorporating a rib 46 that bifurcates the impingement area formed by the respective arrangement of the holes 48, 50, 52, the effect of the collapse of the two-dimensional crossflow on the local heat transfer coefficient is reduced. . This also helps to reduce the deformation of the plate due to the pressure ratio across the plate 40, as well as the centrifugal load due to the effects of the rotating field.
[0024]
In addition to the cooling configuration and the optimized orifice arrangement and impingement plate configuration, the walls of the platform 14 itself are optimized by varying the wall thickness configuration. In order to balance the stress distribution in the pressure side of the platform and the airfoil-to-platform fillet area, the thickness of the platform is varied along the axial direction, as best seen in FIG. The thickness of the leading edge of the platform is uniformly thinner (eg, 0.160 inches), the thickness of the trailing edge of the platform is uniformly thicker (eg, 0.380 inches), and the thickness around the center of the platform is reduced. Experiments have shown that varying between these thicknesses is the best configuration.
[0025]
Combining this particular platform geometry with the cooling arrangement described above would provide the best LCF life.
[0026]
Although the present invention has been described in terms of what is presently considered to be the most practical and preferred embodiments, the present invention should not be limited to the disclosed embodiments, but rather, the spirit and scope of the following claims. It is to be understood that various modifications and equivalent arrangements included within the technical scope are intended to be protected.
[Brief description of the drawings]
[0027]
FIG. 1 is a partial front view of a partial cross section of a gas turbine bucket showing an impingement plate inside a hollow shank portion of the bucket.
2 is a plan view of the bucket shown in FIG. 1, showing the impingement plate inside the shank portion of the bucket generally in phantom lines;
FIG. 3 is a plan view of an impingement plate according to the present invention.
FIG. 4 is a partial side sectional view of the bucket shown in FIG. 2;
[Explanation of symbols]
[0028]
10 Turbine bucket 12 Airfoil 14 Platform 15 Airfoil leading edge 16, 18 Angel wing 17 Airfoil trailing edge 24 Shank portion 26 Skirt 28 Dovetail 38 Impingement cooling plate 44 Platform bottom 46 Rib 50 Impingement cooling hole
Claims (15)
ホイール取付け部分（２８）と、
前記プラットホーム（１４）と前記ホイール取付け部分（２８）との間の半径方向位置に配置された中空のシャンク部分（２４）と、を含み、
前記プラットホームが底面（４４）を有し、
複数のインピンジメント冷却孔（４８、５０、５２）を有するインピンジメント冷却プレート（３８）が、前記底面から間隔を置いて前記中空のシャンク部分の内部に配置されている、
ことを特徴とするタービンバケット（１０）。An airfoil (12) extending from the platform (14) and having a high pressure side (30) and a low pressure side (32);
A wheel mounting part (28),
A hollow shank portion (24) located at a radial position between said platform (14) and said wheel mounting portion (28);
Said platform has a bottom surface (44);
An impingement cooling plate (38) having a plurality of impingement cooling holes (48, 50, 52) disposed within the hollow shank portion spaced from the bottom surface;
A turbine bucket (10), characterized in that:
ホイール取付け部分（２８）と、
底面（４４）を有する前記プラットホーム（１４）と前記ホイール取付け部分（２８）との間の半径方向位置に配置された中空のシャンク部分（２４）と、
前記底面のインピンジメント冷却を可能にするための手段と前記中空のシャンク部分から冷却空気を吐出するための手段と、
を含むことを特徴とするガスタービンバケット（１０）。An airfoil (12) extending from the platform (14) and having a high pressure side (30) and a low pressure side (32);
A wheel mounting part (28),
A hollow shank portion (24) located at a radial position between the platform (14) having a bottom surface (44) and the wheel mounting portion (28);
Means for enabling impingement cooling of the bottom surface and means for discharging cooling air from the hollow shank portion,
A gas turbine bucket (10), comprising:
複数のインピンジメント冷却孔（４８、５０、５２）を有するインピンジメント冷却プレート（３８）を、前記プラットホームの底面（４４）から間隔を置いて前記中空のシャンク部分（２４）の内部に固定する段階と、
前記プラットホームに吐出孔（５６）を設ける段階と、
前記インピンジメント冷却孔（４８、５０、５２）と前記プラットホーム（１４）の前記吐出孔（５６）とを通してタービンホイールスペースの空気流を導く段階と、
を含むことを特徴とする方法。A method for cooling a turbine bucket platform (14) located at a radial position between an airfoil (12) and a mounting portion (28) and forming a radially outer wall surface of a hollow shank portion (24). And
Securing an impingement cooling plate (38) having a plurality of impingement cooling holes (48, 50, 52) within the hollow shank portion (24) spaced from a bottom surface (44) of the platform. When,
Providing a discharge hole (56) in the platform;
Directing turbine wheel space airflow through the impingement cooling holes (48, 50, 52) and the discharge holes (56) of the platform (14);
A method comprising:
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US09/739,445 | 2000-12-19 | ||
| US09/739,445 US6478540B2 (en) | 2000-12-19 | 2000-12-19 | Bucket platform cooling scheme and related method |
| PCT/US2001/025947 WO2002050402A1 (en) | 2000-12-19 | 2001-08-20 | Impingement cooling scheme for platform of turbine bucket |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| JP2004521219A true JP2004521219A (en) | 2004-07-15 |
| JP2004521219A5 JP2004521219A5 (en) | 2008-10-09 |
| JP4738715B2 JP4738715B2 (en) | 2011-08-03 |
Family
ID=24972338
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2002551268A Expired - Lifetime JP4738715B2 (en) | 2000-12-19 | 2001-08-20 | Turbine bucket platform impingement cooling system |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6478540B2 (en) |
| EP (1) | EP1346131B1 (en) |
| JP (1) | JP4738715B2 (en) |
| KR (1) | KR100814168B1 (en) |
| CZ (1) | CZ300480B6 (en) |
| WO (1) | WO2002050402A1 (en) |
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| JP2009047177A (en) * | 2005-05-27 | 2009-03-05 | Mitsubishi Heavy Ind Ltd | Gas turbine moving blade having platform and method for forming same |
| JP2012077749A (en) * | 2010-09-30 | 2012-04-19 | General Electric Co <Ge> | Apparatus and method for cooling platform region of turbine rotor blade |
| JP2012097746A (en) * | 2010-11-04 | 2012-05-24 | General Electric Co <Ge> | System and method for cooling turbine bucket |
| JP2019023465A (en) * | 2017-06-13 | 2019-02-14 | ゼネラル・エレクトリック・カンパニイ | Platform cooling arrangement in turbine component, and method of creating platform cooling arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1346131A1 (en) | 2003-09-24 |
| CZ20031542A3 (en) | 2003-10-15 |
| KR100814168B1 (en) | 2008-03-14 |
| EP1346131B1 (en) | 2013-05-08 |
| JP4738715B2 (en) | 2011-08-03 |
| US20020076324A1 (en) | 2002-06-20 |
| US6478540B2 (en) | 2002-11-12 |
| CZ300480B6 (en) | 2009-05-27 |
| KR20030076994A (en) | 2003-09-29 |
| WO2002050402A1 (en) | 2002-06-27 |
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